CN106795769A - With two gas turbines for cooling down the eddy flow supply line of rotor - Google Patents
With two gas turbines for cooling down the eddy flow supply line of rotor Download PDFInfo
- Publication number
- CN106795769A CN106795769A CN201580054810.8A CN201580054810A CN106795769A CN 106795769 A CN106795769 A CN 106795769A CN 201580054810 A CN201580054810 A CN 201580054810A CN 106795769 A CN106795769 A CN 106795769A
- Authority
- CN
- China
- Prior art keywords
- eddy flow
- supply line
- cooling fluid
- flow supply
- rotor
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
- F01D5/084—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades the fluid circulating at the periphery of a multistage rotor, e.g. of drum type
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
- F01D5/087—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor in the radial passages of the rotor disc
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/16—Control of working fluid flow
- F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
Abstract
The present invention relates to a kind of gas turbine (1), including at least one rotor (2) and inner shell sections (3), to form doughnut (4) between rotor (2) and inner shell sections (3).Doughnut (4) is fluidly connected to compressor portion (5) and is fluidly connected to expansion turbine portion (6) in the other end at one end, and doughnut (4) is designed to supply cooling fluid (8), cooling fluid (8) allows to cool down rotor (2) when gas turbine (1) is operated.In addition, the first eddy flow supply line (11) and the second eddy flow supply line (12) are provided with, the first eddy flow supply line (11) and the second eddy flow supply line (12) are designed to supply cooling fluid (8) to doughnut (4).Cooling fluid (8) is supplied to the surface of rotor (2) with tangential flow component, and is provided as first potted component (13) of flow resistance in addition in doughnut (4), between the first eddy flow supply pipeline (11) and the second eddy flow supply line (12).In addition, discharge pipe (15) is provided with rotor (2), between the first potted component (13) and expansion turbine portion (6), the discharge pipe is designed to that cooling fluid (8) is received and discharged from the second eddy flow supply line (12).Being not provided with can be from the bypass line of the first eddy flow feeding pipe (11) conduction cooling fluid (8), so that the cooling fluid (8) conducted by this way is conducted around the second eddy flow supply pipeline (12), to return to the position of doughnut (4).
Description
Technical field
The present invention relates to a kind of gas turbine, it has at least one rotor and inner shell sections, in rotor and inner casing
Ring is formed between part, its middle ring is designed to supply cooling fluid, and the cooling fluid allows rotor in the operation of gas turbine
Period is cooled.
Background technology
Gas temperature high during due to burn operation in the gas turbine is, it is necessary to suitably cool down multiple function parts
Part.Particularly in the region of the central section of gas turbine, the hot gas for coming from burning from combustion chamber in this region
Interacted, it is necessary to effectively cool down the rotor of rotation with multiple parts.This cooling is generally by the longitudinal direction in rotor
The ring of upper extension is carried out, and cooling fluid (typically compressed air) is introduced in ring, to exhaust through pipeline from ring
Outside distributes heat energy.
Substantially, two function distributions are given the cooling fluid being incorporated into ring.It is cold in addition to the refrigerating function of rotor
But fluid is additionally operable to cool down the rotor blade of expansion turbine, wherein therefore, cooling fluid is by the suitable discharge pipe in rotor
Line is conducted towards the rotor blade of expansion turbine.It is transferred in the related discharge pipe of rotor for by cooling fluid, so
And it is necessary that the transfer at discharge pipe opening is made great efforts or enters effort small as much as possible.Therefore, cooling fluid is most of
In the case of ring is introduced by streaming system of prewhirling, the system correspondingly tangentially accelerates cooling fluid in the direction of motion of rotor
To its surface.It is desirable that making cooling fluid reach the peripheral speed of rotor, discharge pipe opening is being transferred to such that it is able to save
The additional entrance effort of period.In order to shift, cooling fluid is generally from the eddy flow supply pipe of the streaming system of prewhirling being suitably formed
Line is discharged, and through ring on its laterally (perpendicular to the longitudinal direction of rotor), and is fed to discharge pipe in the rotor
Opening.
Tangential flow adjustment due to cooling fluid relative to rotor surface, is greatly reduced or even prevents mechanical rotor
Power is transferred to cooling fluid and produces heat.When being discharged from eddy flow supply line, cooling fluid in heat in itself so as to adjust
Nodular state, the thermal conditioning state is particularly well-suited to the radiating on rotor surface to be cooled, so as to have due to rotor-fluid friction
Local temperature declines without heating cooling fluid caused by significant negative effect, and heat is transferred into cooling fluid can have
Carry out to effect.In order to the heat loss of rotor can be suitably dispersed into outside after corresponding heat transfer, it is desirable to be able to
Controlled mode discharges cooling fluid from ring.
For example described in the B1 of EP 1 537 296 for cooling down rotor and for by cooling fluid feeding rotor
This loop systems of access road.A kind of ring is which described, wherein cooling fluid is flowed into from two eddy flow supply lines respectively
Ring, or it is transferred to the corresponding entrance opening of cooling fluid discharge pipe in rotor.Two eddy flow supply lines are designed to use
Yu Xianghuan supplies cooling fluid, and wherein cooling fluid is applied by the components of flow in the tangential direction to the surface of the rotor
Effect, and wherein the first eddy flow supply line and the second eddy flow supply line be also by multiple potted components each other fluidly
Separate.Therefore, the entrance of the discharge pipe for cooling fluid being transferred into rotor from the second eddy flow supply line for without prejudice to is opened
In mouthful, therefore, the invention of prior art is provided installs bypass line, and it makes cooling fluid bypass the second eddy flow supply line to arrive
In ring.As the result of by-pass line, between the entrance opening of the discharge pipe in the second eddy flow supply line and rotor
There is relatively low interference crossing current in the region for intersecting section, be effectively transferred to turn such that it is able to enter to be about to cooling fluid
Son.
However, from the shortcoming of the embodiment known in the art be first at a relatively high technical costs because shunt valve
Line must be built in the inner shell sections of gas turbine.Additionally, in the case of known solution from the prior art, also
Occur in that the dead space being formed between the first and second eddy flow supply lines, and wherein rotor cooling first by cooling down stream
The convection current of body is carried out.However, this makes only to obtain unsatisfactory cooling in the section of the restriction dead space of rotor, and
And therefore cause rotor in the height heating of some regions, however, this needs is avoided.
It is associated with these shortcomings of prior art, therefore proposes and a kind of can avoid shortcoming known in the art
The technical requirements of gas turbine.Especially, the gas turbine to be proposed is can advantageously to cool down the part for limiting ring, but is not required to
Want technical fee high.Above all, it is to avoid the dead space in the ring that some regions cause different cooling rate.
The content of the invention
These purposes that the present invention is based on are realized by gas turbine according to claim 1.
The purpose that the present invention is based on realizes particularly by gas turbine, and gas turbine has at least one rotor and interior
Shell parts, for forming ring between rotor and inner shell sections, wherein at one end ring be fluidly connected to compressor section and
Expansion turbine section is fluidly connected in the other end, wherein the ring design is into supply cooling fluid, the cooling fluid is allowed
Rotor is cooled during the operation of gas turbine, and also provides the first eddy flow supply line and the second eddy flow supply line,
First eddy flow supply line and the second eddy flow supply line are designed to supply cooling fluid to the ring, wherein the cooling
Fluid is acted on by the components of flow applying in the tangential direction to the surface of the rotor, and in the first rotation wherein in ring
The first potted component of flow resistance is also provided as between stream supply line and the second eddy flow supply line, wherein in the rotor
Discharge pipe is also set up between the first potted component and expansion turbine section, discharge pipe is designed to be supplied from the second eddy flow
Answer pipeline to receive and discharge cooling fluid, and be wherein not provided with for conducting cold from the first eddy flow supply line as follows
But the by-pass line of fluid so that the cooling fluid thus conducted is conducted around the second eddy flow supply line, to supply again
To the position of ring.
According to the present invention, " rotor " one word refers to all rotating parts of gas turbine rotor component, and they produce ring
Border.In this case, also particularly including gas turbine rotor component disk and distance piece.
According to the present invention, thus provide by potted component by ring be subdivided into two each other fluid separate regions,
Wherein cooling fluid is supplied in first area by the first eddy flow supply line first and second area passes through the second eddy flow first
Supply line supplies cooling fluid.However, in this case, being clearly not provided with the second eddy flow supply pipe infarctional
The by-pass line of cooling fluid, so as to correspondingly reduce technical costs, and cooling fluid is in the whole surface for forming ring
Refrigerating function can ensure.
In order to realize the effective cooling to the surface of revolution of rotor, cooling fluid is transmitted via two eddy flow supply lines
To in ring, the respective regions that fluid is separate each other are flowed into.By potted component, ring is subdivided into two can largely be divided
Turn up the soil and realize the region of above-mentioned two function.(in this region, it is not provided with for cooling fluid being transferred to rotor in following region
Discharge pipe entrance opening for cooling fluid is transported on the rotor blade of expansion turbine), can be effective for ring
Almost exclusive refrigerating function for rotor surface is provided.However, in another region of ring, lateral flow is considered as,
Flowing i.e. on the longitudinal direction of ring, its cooling fluid with the entrance opening of the discharge pipe for being transferred into rotor is fluidly
Interact.Interaction causes cooling fluid to enter the slightly lower transfer efficiency of discharge pipe entrance opening, but in order to change
Enter the heat cooling of rotor surface, this point can be received.Additionally, the cooling fluid with the entrance opening for being transferred to discharge pipe
Amount of the horizontal flow of interaction preferably than the cooling fluid relative to the entrance opening for being transferred to discharge pipe is smaller, makes
There is small loss in efficiency during must shifting.
Additionally, allowing the matter of the cooling fluid in independent regulation ring respective regions using two eddy flow supply lines of separation
Amount flow and pressure.By the first potted component of appropriate selection, it is also possible to which the mode for substantially improving is to the corresponding of cooling fluid
Function carries out appropriate regulation.
At this point it should be noted that presently described gas turbine is preferably only stationary gas wheel first
Machine.Inner shell sections are generally configured shaft-cup so that ring is formed between the rotating part and shaft-cup of rotor.
Due to according to the present invention, being not provided with the bypass line for bypassing the second eddy flow supply line, will not also be formed only
Have to be cooled down by convection current and can just make the surface-cooled dead space of rotary part.Conversely, by the tangent line side of rotor surface
Upward rotation cooling fluid stream, whole ring is effectively cooled in two regions limited by the first potted component.
Meanwhile, the carrying out of respective regions that can be to by the first potted component separate is satisfactorily separated so that energy
Two function phases are enough realized to efficiently separating, the two functions particularly cool down rotor surface and are transferred to cooling fluid
The entrance opening of sub- discharge pipe.Further, since the flowing of the longitudinal direction across the ring of the second potted component, it is possible to achieve phase
Close the sufficient surface cooling of the moving component of rotor in region.
According to the first particularly preferred embodiment, the second potted component, the second potted component arrangement are additionally provided in ring
Between the second eddy flow supply line and expansion turbine section.Second potted component is typically provided at the discharge pipe in rotor
And expansion turbine section between.In this case, the second potted component substantially prevent cooling fluid and expansion turbine area
The exchange of the adjacent area of section, such that it is able to greatly reduce the loss of cooling fluid.
Additionally, according to embodiment, can be by the region between the first potted component and the second potted component largely
Minimize so that the region is initially used for being transported to cooling fluid in the entrance opening of the discharge pipe in rotor.By first
The region for the ring limited with the second potted component can in particular than being limited by the first potted component and compressor section
The smaller design in other areas, especially 1/5th on the direction of the longitudinal extent of ring are even more small.Due to cooling fluid
Relative to the favourable tangential velocity of the rotor surface between the first and second potted components, relatively less kinetic energy is added to
In cooling fluid, energy transmission loss as a result can be reduced.Because power transfer losses are reduced, the temperature of cooling fluid is relatively
It is low so that the cooling capacity in the region is also relatively large.As a result it is also more effective in addition to improving gas turbine proficiency level
Cooling level.
According to the continuity that this is conceived, discharge pipe is radially arranged in the rotor.The entrance opening of exhaust line is particularly
It is radially arranged in the rotor.As a result, the embodiment is especially different from and the axial embodiment for generally needing greater room requirement.
For example from axial embodiment known to the known in the literature document above for prior art, in other words, for cooling to be flowed
Body from the second eddy flow supply line be in axial direction transferred to rotor in discharge pipe entrance opening in.Due to discharge pipe
Radial arrangement, it is also possible to effectively prevent dead space, the sizeable proportion that convection current cooling is accounted in overall cooling in dead space.
According to another preferred embodiment of the invention, there is provided, the obstruction free flow area of the second eddy flow supply line is big
In the effective flowing cross section of the first eddy flow supply line.In this case, effective flow cross section is average or average
Flow cross section, thus defines the flow of the cooling fluid of time per unit.In this respect, it can be ensured that from the second eddy flow
Supply line for be transferred to the cooling fluid in the entrance opening of the discharge pipe of rotor along longitudinal direction only in the journey of very little
Degree is influenceed by the lateral flow on the surface along rotor.Furthermore, it is possible to set up pressure ratio in this way so that first
Potted component has than the first potted component on the side for pointing to compressor section towards the region at expansion turbine section
Static pressure static pressure higher.Result of which, the first eddy flow supply line that flows through of only relatively small ratio enters
Cooling fluid in ring flows through the first potted component so that in ring, between compressor section and the first potted component, backflow
Can substantially be produced towards compressor section.Therefore, flow back on the direction oriented towards compressor against in gas turbine
Hot gas main flow and transmit.
According to another preferred embodiment of the invention, there is provided, the first eddy flow supply line and the second eddy flow supply pipe
The ratio of the effective flowing cross section of line is chosen to during the operation of gas turbine, less than 10% by the first rotation
The cooling fluid of stream supply line conduction also flows through the first potted component.In this respect, ring is flowed into from the first eddy flow supply line
Cooling fluid of the relatively small number of cooling fluid in ring is fed to from the second eddy flow supply line mix.In this respect, come
Also only influenceed by fairly small from the tangential flow component of the cooling fluid of the second eddy flow supply line.
Because the pressure in the first eddy flow supply line region compared with compressor portion is higher, may insure in addition in the first rotation
Can be formed along the backflow of the length direction of ring between stream supply line and compressor section so that realize limiting the part of ring
Effectively cooling.In this case, the cooling fluid being fed back into can reenter compressor in the region of compressor section,
And discharged from compressor again after possible compression.
According to another preferred embodiment of the invention, there is provided, the end of the ring being associated with compressor section is set
Count into and cause during gas turbine operation, cooling fluid can be transferred to the region of the last rotor blade row of compressor
In.Result of which, the cooling fluid being incorporated into ring by the first eddy flow supply line is transferred again in compressor,
So that can substantially form a circulation.Cooling fluid is discharged from compressor, is particularly discharged again in a compressed format, and can
The first eddy flow supply line is fed to again.Circulated as by being formed, can effectively prevent the stream of cooling fluid
Lose, as a result also can during operation keep gas turbine proficiency higher.
Another particularly preferred embodiment of the invention, there is provided, the first eddy flow supply line and the second eddy flow
Supply line is all disposed within inner shell sections.
Another particularly preferred embodiment of the invention, there is provided, the first eddy flow supply line and the second eddy flow
Supply line is in fluid communication with same room, to supply cooling fluid at the same pressure.Therefore, two eddy flow supply lines from
Identical cooling fluid holder feeds so that the pressure in the respective regions of ring sets and can easily pass through corresponding eddy flow
The appropriate geometry of supply line and potted component is carried out.
Brief description of the drawings
Describe the present invention in detail below with reference to accompanying drawings.In this case, the figure is should refer to only by schematically geographical
Solution, and this is practiced without limitation for of the invention.
The all technical characteristics with identical reference shown in figure, with identical technique effect.
In addition it is noted that claiming the optional combination of the then technical characteristic of description in the present case, as long as this
A little combinations can realize the purpose of institute's foundation of the present invention.
In this case, in figure：
Fig. 1 shows the sectional view of the ring that gas turbine of the invention is passed through along the longitudinal direction of gas turbine.
Specific embodiment
This graph show that along the sectional view in a longitudinal direction of ring 4 of gas turbine of the invention 1.In this feelings
Under condition, ring 4 is limited by compressor section 5 and expansion turbine section 6 respectively in end, and is arranged in (the usual shape of inner shell sections 3
As shaft-cup) and rotor 2 between.The part of rotor 2 performs rotary motion during the operation of gas turbine 1 so that their phases
Moved (remove outside the plane of paper or enter in the plane of paper) for static inner shell sections 3.
Due in region high temperature prevailing, it is therefore desirable to cool down inner shell sections 3 and rotor 2, so as in these regions
Correspondingly distribute heat.Cooling is carried out by cooling fluid 8, and cooling fluid 8 is in this case compressor air 10, wherein
Compressor air 10 is discharged in the region of blower outlet 22 and slowed down in the region of diffuser 23.During due to slowing down,
Of a relatively high static pressure is established, by the static pressure, compressor air 10 is by can be with after another opening 7 in housing
It is transferred to suitable plenum chamber 9.Plenum chamber 9 is used as the holder of compressor air 10, to use (the compressor of cooling fluid 8
Air 10) supply the two eddy flow supply lines 11 and 12 being in fluid communication with ring 4.
Two eddy flow supply lines 11 and 12 allow cooling fluid 8 be transferred to respectively ring 4 by the first potted component 13
In the region of separation, two of which function is substantially performed by cooling fluid 8.On the one hand, cooling fluid 8 is used for from restriction ring
The top surface radiating of 4 part, on the other hand, cooling fluid 8 (has and does not provide accompanying drawing mark for being transferred into discharge pipe 15
The entrance opening of note) in the channel system 28 in rotor 2.Therefore, channel system 28 allows cooling fluid 8 to be fed to expansion
The first rotor blade row 26 of turbine, for cooling purposes.
In order to cooling fluid 8 to be transferred to the entrance of discharge pipe 15 as efficiently as possible from the second eddy flow supply line 12
Opening, cooling fluid 8 is acted on by the second eddy flow supply line 12 with tangential motion component, and the tangential component allows cold
But fluid 8 flows from after the discharge of the second eddy flow supply line 12 substantially on the circumferencial direction of rotor surface.As this
The result that sample does, largely avoids cooling fluid 8 and is being transferred to the entrance opening phase of rotor discharge pipe 15 in itself
Between the effect that must be acted on by corresponding component motion, otherwise rotor 2 will correspondingly be deprived of rotating energy.With the second eddy flow
The region of the associated ring 4 of supply line 12 is sealed in end respectively by potted component 13 and 14.In this respect, can be with
Ensuring the cooling fluid 8 fed by the second eddy flow supply line 12 of higher proportion can be transferred in discharge pipe 15.
However, the cooling fluid 8 of small percentage flows through the second potted component 14 on the longitudinal direction of ring 4 enters expansion turbine area
In section 6.Cooling fluid 8 is discharged together with the hot gas of the gas turbine 1 expanded in from expansion turbine therefrom.
Additionally, cooling fluid 8 is fed to ring via the first eddy flow supply line 11.Cooling fluid 8 is in this case
The region between the first potted component 13 and compressor section 5 is flowed into, backflow is formed wherein so that cooling fluid stream is in ring 4
In flow to compressor from the first eddy flow supply line 11.The part that the cooling fluid stream is only used for from the region for limiting ring 4 is defeated
Send heat.After cooling fluid 8 is transferred in compressor section 5, cooling fluid 8 after compression is updated, as calming the anger
Machine air 10 is fed to diffuser 23 via blower outlet 22.In this respect, can be supplied in the eddy flow of compressor section 5 and first
To answer set up between pipeline 11 and circulate, and the heat in the region associated respectively from ring 4 can be effectively dissipated.
According to the setting of the first eddy flow supply line 11 or the flow cross section of the second eddy flow supply line 12, and according to
The sealing effectiveness of the first potted component 13 or the second potted component 14, it can be advantageous to which foundation is separated by the first potted component 13
Ring 4 two regions in flow-rate ratio so that the backflow of such as cooling fluid 10 towards compressor section 5 can also set up.
Other embodiment is defined from dependent claims.
Claims (9)
1. a kind of gas turbine (1), with least one rotor (2) and enclosure interior (3), in rotor (2) and inner casing portion
Divide formation ring (4) between (3), wherein the ring (4) is fluidly connected to compressor section (5) and in the other end at one end
Place is fluidly connected to expansion turbine section (6), wherein the ring (4) is designed to supply cooling fluid (8), the cooling fluid
Permission cools down the rotor (2) during the operation of the gas turbine (1), and is wherein also provided with the first eddy flow supply pipe
Line (11) and the second eddy flow supply line (12), the first eddy flow supply line (11) and the second eddy flow supply line
(12) it is designed to for cooling fluid (8) to be supplied to the ring (4), wherein the cooling fluid (8) is by the rotor
(2) the components of flow applying effect in the tangential direction on surface, and wherein in the ring (4), in first eddy flow
First potted component (13) of flow resistance is provided as between supply line (11) and the second eddy flow supply line (12),
Discharge pipe is set wherein in the rotor (2), between first potted component (13) and the expansion turbine section (6)
Line (15), the discharge pipe (15) is designed to receive and discharge cooling fluid from the second eddy flow supply line (12)
(8), it is characterised in that
It is not provided with being conducted from the first eddy flow supply line (11) as follows the bypass line of cooling fluid (8),
So that the cooling fluid (8) thus conducted is conducted to be fed to institute again around the second eddy flow supply line (12)
State the position of ring (4).
2. gas turbine according to claim 1, it is characterised in that
The second potted component (14) is also set up in the ring (4), second potted component is disposed in second eddy flow
Between supply line (12) and the expansion turbine section (6).
3. gas turbine according to claim 2, it is characterised in that
The discharge pipe (15) is arranged radially in the rotor (2).
4. gas turbine according to any one of the preceding claims, it is characterised in that
The effective flowing cross section of the second eddy flow supply line (12) is more effective than the first eddy flow supply line (11)
Flow cross section is big.
5. gas turbine according to any one of the preceding claims, it is characterised in that
The ratio of the effective flowing cross-sectional area of the first eddy flow supply line (11) and the second eddy flow supply line (12)
Example is selected such that during the operation of the gas turbine (1) first eddy flow that is conducted through less than 10% is supplied
The cooling fluid (8) of pipeline (11) flows through first potted component (13).
6. gas turbine according to any one of the preceding claims, it is characterised in that
During the operation of the gas turbine (1), the first eddy flow supply line (11) towards the ring (4) outlet
The static pressure at place is more than the static pressure in the ring (4) at the compressor section (5) place.
7. gas turbine according to any one of the preceding claims, it is characterised in that
The end of the ring (4) being associated with the compressor section (5) is designed such that in the gas turbine (1)
During operation, cooling fluid (8) can be transferred to the region of last rotor blade row (21) of the compressor (20)
In.
8. gas turbine according to any one of the preceding claims, it is characterised in that
Both the first eddy flow supply line (11) and the second eddy flow supply line (12) are all disposed within the inner casing portion
Divide in (3).
9. gas turbine according to any one of the preceding claims, it is characterised in that
The first eddy flow supply line (11) and the second eddy flow supply line both with identical plenum chamber (9) fluid
Connection, for providing cooling fluid (8) at the same pressure.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP14187954.4A EP3006668A1 (en) | 2014-10-07 | 2014-10-07 | Gas turbine with two vortex feeds for cooling the rotor |
| EP14187954.4 | 2014-10-07 | ||
| PCT/EP2015/072709 WO2016055354A1 (en) | 2014-10-07 | 2015-10-01 | Gas turbine with two swirl supply lines for cooling the rotor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106795769A true CN106795769A (en) | 2017-05-31 |
| CN106795769B CN106795769B (en) | 2019-05-31 |
Family
ID=51659585
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201580054810.8A Expired - Fee Related CN106795769B (en) | 2014-10-07 | 2015-10-01 | There are two the gas turbines of the eddy flow supply line for cooling down rotor for band |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US10036256B2 (en) |
| EP (1) | EP3006668A1 (en) |
| JP (1) | JP6282784B2 (en) |
| CN (1) | CN106795769B (en) |
| WO (1) | WO2016055354A1 (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11377957B2 (en) * | 2017-05-09 | 2022-07-05 | General Electric Company | Gas turbine engine with a diffuser cavity cooled compressor |
| US10982546B2 (en) | 2018-09-19 | 2021-04-20 | General Electric Company | Flow-diverting systems for gas turbine air separator |
| US11674396B2 (en) | 2021-07-30 | 2023-06-13 | General Electric Company | Cooling air delivery assembly |
| EP4174286A1 (en) | 2021-10-29 | 2023-05-03 | ANSALDO ENERGIA S.p.A. | Gas turbine assembly for power plant with improved rotor and turbine blades cooling and method for operating this gas turbine assembly |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4291531A (en) * | 1978-04-06 | 1981-09-29 | Rolls-Royce Limited | Gas turbine engine |
| EP1057976A1 (en) * | 1999-05-24 | 2000-12-06 | General Electric Company | Rotating seal |
| US20110250057A1 (en) * | 2010-04-12 | 2011-10-13 | Laurello Vincent P | Radial pre-swirl assembly and cooling fluid metering structure for a gas turbine engine |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4433289A1 (en) * | 1994-09-19 | 1996-03-21 | Abb Management Ag | Axial gas turbine |
| US6672072B1 (en) | 1998-08-17 | 2004-01-06 | General Electric Company | Pressure boosted compressor cooling system |
| US6773225B2 (en) * | 2002-05-30 | 2004-08-10 | Mitsubishi Heavy Industries, Ltd. | Gas turbine and method of bleeding gas therefrom |
| US6837676B2 (en) * | 2002-09-11 | 2005-01-04 | Mitsubishi Heavy Industries, Ltd. | Gas turbine |
| DE102005025244A1 (en) | 2005-05-31 | 2006-12-07 | Rolls-Royce Deutschland Ltd & Co Kg | Air guiding system between compressor and turbine for gas-turbine engine operated at high pressure ratio has compressor and air chamber whereby first turbine cooling air is flowed through air chamber |
| JP5502340B2 (en) * | 2009-02-25 | 2014-05-28 | 三菱重工業株式会社 | Turbine cooling structure and gas turbine |
| CN106460669B (en) * | 2014-06-04 | 2018-05-01 | 三菱日立电力***株式会社 | Gas turbine |
-
2014
- 2014-10-07 EP EP14187954.4A patent/EP3006668A1/en not_active Withdrawn
-
2015
- 2015-10-01 CN CN201580054810.8A patent/CN106795769B/en not_active Expired - Fee Related
- 2015-10-01 WO PCT/EP2015/072709 patent/WO2016055354A1/en active Application Filing
- 2015-10-01 US US15/514,763 patent/US10036256B2/en not_active Expired - Fee Related
- 2015-10-01 JP JP2017518510A patent/JP6282784B2/en not_active Expired - Fee Related
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4291531A (en) * | 1978-04-06 | 1981-09-29 | Rolls-Royce Limited | Gas turbine engine |
| EP1057976A1 (en) * | 1999-05-24 | 2000-12-06 | General Electric Company | Rotating seal |
| US20110250057A1 (en) * | 2010-04-12 | 2011-10-13 | Laurello Vincent P | Radial pre-swirl assembly and cooling fluid metering structure for a gas turbine engine |
Also Published As
| Publication number | Publication date |
|---|---|
| US20170218771A1 (en) | 2017-08-03 |
| WO2016055354A1 (en) | 2016-04-14 |
| JP2017531127A (en) | 2017-10-19 |
| US10036256B2 (en) | 2018-07-31 |
| CN106795769B (en) | 2019-05-31 |
| EP3006668A1 (en) | 2016-04-13 |
| JP6282784B2 (en) | 2018-02-21 |
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